MIL-DTL-19328F
3.2.2.4 Exterior coating. After the cleaning specified (see 3.4) has been completed, the assembled liquid
oxygen container and any parts of the other components that are to be painted shall be coated with a primer
compatible with the finish to be applied. One or more coats of durable, high quality paint shall be applied as
required to achieve a smooth protective finish free of cracks, checks, or runs. The color of the topcoat shall
conform to 14187 of FED-STD-595. Organic finishes shall be applied in accordance with MIL-F-18264.
3.2.2.5 Protective treatment. When materials are used in the construction of the converter that are subject to
deterioration when exposed to environmental conditions likely to occur during service usage, they shall be
protected against such deterioration in a manner that will in no way prevent compliance with the performance
requirements of this specification. Protective coating which might crack, chip or scale during normal service life
or under extremes of environmental conditions shall not be used.
3.2.3 Tubing and fittings. All openings of the finished converter shall be capped or plugged to prevent thread
damage and to prevent the entry of moisture and foreign matter. Aluminum tubing that interconnects components
shall be double flared to conform to MS33583. Tube fittings and pipe thread bosses for mating the converter to
aircraft lines shall be corrosion-resistant steel. Corrosion-resistant steel tubing shall be single flared to conform to
MS33584.
3.2.4 Antiseize tape. Antiseize tape shall be used on all male pipe thread fittings. Antiseize tape shall
conform to and shall be applied as specified in MIL-T-27730. Tape shall not be used on flare tube fittings, straight
threads, coupling sleeves, or on the outer side of tube flares. None of the tape shall be allowed to enter the inside
of a fitting.
3.2.5 Check valves and flow restrictors. Check valves and flow restrictors may be used in the circuit as
required for function. Check valves and flow restrictors shall be spring loaded as necessary to avoid any
possibility of entrapment of liquid oxygen in a dead end circuit.
3.2.6 Shock mounts. Shock mounts (if provided) and sway clearance due to shock mounting shall be within
the specified envelope.
3.2.7 Standard parts. Standard component parts usually used in the aerospace industry shall be encouraged,
provided they suit the intended purpose.
3.2.8 Threads. Screw threads shall be in accordance with MIL-S-7742. Pipe threads shall be in accordance
with MIL-P-7105.
3.2.9 Dimensions. The dimensions of the converter shall be as specified in figures 1, 2, 3, 4.
3.3 Details of components.
3.3.1 Liquid oxygen container. The liquid oxygen container shall be designed to contain a minimum of 5
liters of liquid oxygen measured at 1 atmosphere (101.3 kPa). The container shall be designed such that in case of
contamination the container can be easily and completely cleaned by Overhaul and Repair servicing personnel and
then returned to service status. If the container employs a vacuumed space as insulation, it shall be provided with
a functional adsorbent. The container shall be baffled to prevent direct exit of liquid oxygen through the vent line
during initial stages of the filling operation.
3.3.2 Container outer shell. The outer shell of the container shall be provided with a rupture point having not
less than a 0.375 inch (9.525 mm) diameter escape area. Pressure required to rupture the escape area shall be at
least 20 percent less than the burst pressure of the outer container shell. The rupture point shall be located in such
a position that in case of rupture the danger to personnel will be at a minimum.
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